Transition duct assembly with late injection features

Abstract

A turbomachine includes a plurality of transition ducts disposed in a generally annular array. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each of the plurality of transition ducts is offset from the inlet along the longitudinal axis and the tangential axis. The turbomachine includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path, and a plurality of mechanical fasteners connecting at least one transition duct of the plurality of transition ducts to the support ring assembly. The turbomachine includes a late injection assembly providing fluid communication for an injection fluid to flow into the interior downstream of the inlet of at least one transition duct of the plurality of transition ducts.

What is claimed is: 
     
       1. A turbomachine comprising:
 a plurality of transition ducts disposed in a generally annular array and comprising a first transition duct and a second transition duct, each of the plurality of transition ducts comprising an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis, the outlet of each of the plurality of transition ducts offset from the inlet along the longitudinal axis and the tangential axis; 
 a support ring assembly downstream of the outlet of each of the plurality of transition ducts along a hot gas path, the support ring assembly defining a transition between the outlet of each of the transition ducts and a first stage bucket assembly and further defining an injection fluid flow passage therethrough; 
 a plurality of mechanical fasteners connecting each transition duct of the plurality of transition ducts to the support ring assembly; and 
 a late injection assembly disposed radially outward of the support ring assembly and providing fluid communication for an injection fluid to flow through the injection fluid flow passage into the interior of at least one transition duct of the plurality of transition ducts, wherein an outlet of the late injection assembly is defined downstream of a choke plane defined in the interior of the at least one transition duct. 
 
     
     
       2. The turbomachine of  claim 1 , wherein the late injection assembly comprises an inlet tube and a fuel port providing fluid communication for flowing a fuel into the inlet tube. 
     
     
       3. The turbomachine of  claim 2 , wherein the late injection assembly further comprises a fuel conduit in fluid communication with the inlet tube through the fuel port. 
     
     
       4. The turbomachine of  claim 2 , wherein an inlet of the inlet tube is configured to flow a working fluid into the inlet tube. 
     
     
       5. The turbomachine of  claim 2 , wherein the flow passage through the support ring assembly comprises a first conduit; and wherein a second conduit extending extends through the transition duct, the first conduit being in fluid communication with the second conduit. 
     
     
       6. The turbomachine of  claim 5 , wherein the first conduit and the second conduit are in direct fluid communication. 
     
     
       7. The turbomachine of  claim 5 , wherein the flow passage through the support ring assembly further defines a manifold, the manifold being disposed in fluid communication between the first conduit and the second conduit. 
     
     
       8. The turbomachine of  claim 1 , wherein an inner surface of the at least one transition duct at least partially defines a trailing edge, and wherein the outlet of the late injection assembly is defined in the trailing edge. 
     
     
       9. The turbomachine of  claim 1 , wherein an inner surface of the at least one transition duct at least partially defines a pressure side and a suction side, and wherein the outlet of the late injection assembly is defined in one of the pressure side or the suction side. 
     
     
       10. The turbomachine of  claim 1 , wherein the outlet of each of the plurality of transition ducts is further offset from the inlet along the radial axis. 
     
     
       11. The turbomachine of  claim 1 , further comprising a turbine section in communication with plurality of transition ducts, the turbine section comprising the support ring assembly and the first stage bucket assembly. 
     
     
       12. The turbomachine of  claim 11 , wherein no nozzles are disposed upstream of the first stage bucket assembly. 
     
     
       13. A turbomachine comprising:
 a plurality of transition ducts disposed in a generally annular array and comprising a first transition duct and a second transition duct, each of the plurality of transition ducts comprising an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis, the outlet of each of the plurality of transition ducts offset from the inlet along the longitudinal axis and the tangential axis, the outlet of each of the plurality of transition ducts comprising a first mounting flange and a second mounting flange spaced from the first mounting flange along the radial axis; 
 a support ring assembly downstream of the outlet of each of the plurality of transition ducts along a hot gas path, the support ring assembly defining a transition between the outlet of each of the transition ducts and a first stage bucket assembly and further defining an injection fluid flow passage therethrough, the support ring assembly comprising an inner support ring and an outer support ring; 
 a plurality of mechanical fasteners connecting each transition duct of the plurality of transition ducts to the support ring assembly, at least a first mechanical fastener of the plurality of mechanical fasteners extending through the first mounting flange and the inner support ring and at least a second mechanical fastener of the plurality of mechanical fasteners extending through the second mounting flange and the outer support ring; and 
 a late injection assembly disposed radially outward of the support ring assembly and providing fluid communication for an injection fluid to flow into the interior of at least one transition duct of the plurality of transition ducts, wherein an outlet of the late injection assembly is defined downstream of a choke plane defined in the interior of the at least one transition duct. 
 
     
     
       14. The turbomachine of  claim 13 , wherein an inner surface of the at least one transition duct at least partially defines a trailing edge, and wherein the outlet of the late injection assembly is defined in the trailing edge. 
     
     
       15. The turbomachine of  claim 13 , wherein an inner surface of the at least one transition duct at least partially defines a pressure side and a suction side, and wherein the outlet of the late injection assembly is defined in one of the pressure side or the suction side.